[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2003]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR23.147]

[Page 187-188]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 23--AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES--Table of Contents
 
                            Subpart B--Flight
 
Sec. 23.147  Directional and lateral control.

    (a) For each multiengine airplane, it must be possible, while 
holding the wings level within five degrees, to make sudden changes in 
heading safely in both directions. This ability must be shown at 1.4 
VS1 with heading changes up to 15 degrees, except that the 
heading change at which the rudder force corresponds to the limits 
specified in Sec. 23.143 need not be exceeded, with the--
    (1) Critical engine inoperative and its propeller in the minimum 
drag position;
    (2) Remaining engines at maximum continuous power;
    (3) Landing gear--
    (i) Retracted; and
    (ii) Extended; and
    (4) Flaps retracted.
    (b) For each multiengine airplane, it must be possible to regain 
full control of the airplane without exceeding a bank angle of 45 
degrees, reaching a dangerous attitude or encountering dangerous 
characteristics, in the event of a sudden and complete failure of the 
critical engine, making allowance for a delay of two seconds in the 
initiation of recovery action appropriate to the situation, with the 
airplane initially in trim, in the following condition:
    (1) Maximum continuous power on each engine;

[[Page 188]]

    (2) The wing flaps retracted;
    (3) The landing gear retracted;
    (4) A speed equal to that at which compliance with Sec. 23.69(a) has 
been shown; and
    (5) All propeller controls in the position at which compliance with 
Sec. 23.69(a) has been shown.
    (c) For all airplanes, it must be shown that the airplane is safely 
controllable without the use of the primary lateral control system in 
any all-engine configuration(s) and at any speed or altitude within the 
approved operating envelope. It must also be shown that the airplane's 
flight characteristics are not impaired below a level needed to permit 
continued safe flight and the ability to maintain attitudes suitable for 
a controlled landing without exceeding the operational and structural 
limitations of the airplane. If a single failure of any one connecting 
or transmitting link in the lateral control system would also cause the 
loss of additional control system(s), compliance with the above 
requirement must be shown with those additional systems also assumed to 
be inoperative.

[Doc. No. 27807, 61 FR 5188, Feb. 9, 1996]